HQ 3.5/8 AIRFOIL (hq358-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/8 AIRFOIL (hq358-il) Reynolds number: 100,000 Max Cl/Cd: 64.73 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq358-il-100000.txt Download as CSV file: xf-hq358-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3504 0.09448 0.08988 -0.0323 1.0000 0.0608
-7.500 -0.3564 0.09240 0.08789 -0.0311 1.0000 0.0626
-7.250 -0.3664 0.09079 0.08638 -0.0293 1.0000 0.0637
-7.000 -0.3795 0.08935 0.08505 -0.0273 1.0000 0.0647
-6.750 -0.3893 0.08754 0.08333 -0.0271 1.0000 0.0659
-6.500 -0.3971 0.08550 0.08137 -0.0295 1.0000 0.0670
-6.250 -0.3994 0.08296 0.07880 -0.0364 1.0000 0.0679
-6.000 -0.3964 0.08060 0.07625 -0.0424 1.0000 0.0683
-5.750 -0.3988 0.07543 0.07139 -0.0337 1.0000 0.0702
-5.500 -0.3966 0.07279 0.06879 -0.0312 1.0000 0.0726
-5.250 -0.3904 0.06963 0.06562 -0.0324 1.0000 0.0761
-5.000 -0.3640 0.06577 0.06126 -0.0453 1.0000 0.0822
-4.750 -0.3626 0.06142 0.05718 -0.0412 1.0000 0.0842
-4.500 -0.3525 0.05854 0.05432 -0.0405 1.0000 0.0887
-4.250 -0.3271 0.05428 0.04975 -0.0464 1.0000 0.0975
-4.000 -0.3071 0.05168 0.04699 -0.0480 1.0000 0.1079
-3.750 -0.2906 0.04793 0.04325 -0.0488 1.0000 0.1146
-3.500 -0.2676 0.04490 0.04006 -0.0509 1.0000 0.1289
-3.250 -0.2416 0.04210 0.03701 -0.0537 1.0000 0.1528
-3.000 -0.2198 0.03960 0.03444 -0.0547 1.0000 0.1804
-2.250 -0.0953 0.02959 0.02213 -0.0599 1.0000 0.0664
-2.000 -0.0528 0.02707 0.01890 -0.0617 0.9972 0.0559
-1.750 -0.0123 0.02519 0.01685 -0.0644 0.9932 0.0605
-1.500 0.0279 0.02359 0.01486 -0.0660 0.9884 0.0590
-1.250 0.0688 0.02238 0.01351 -0.0680 0.9839 0.0625
-1.000 0.1067 0.02137 0.01244 -0.0697 0.9787 0.0710
-0.750 0.1461 0.01835 0.01165 -0.0725 0.9760 0.5991
-0.500 0.1782 0.01772 0.01148 -0.0716 0.9692 1.0000
-0.250 0.2140 0.01807 0.01148 -0.0737 0.9600 1.0000
0.000 0.2544 0.01850 0.01162 -0.0766 0.9521 1.0000
0.250 0.2949 0.01888 0.01174 -0.0796 0.9438 1.0000
0.500 0.3297 0.01921 0.01190 -0.0814 0.9343 1.0000
0.750 0.3709 0.01953 0.01208 -0.0842 0.9259 1.0000
1.000 0.4155 0.01969 0.01212 -0.0875 0.9162 1.0000
1.250 0.4582 0.01967 0.01202 -0.0901 0.9037 1.0000
1.500 0.5025 0.01950 0.01180 -0.0927 0.8911 1.0000
1.750 0.5430 0.01938 0.01166 -0.0948 0.8794 1.0000
2.000 0.5833 0.01927 0.01158 -0.0968 0.8696 1.0000
2.250 0.6322 0.01889 0.01124 -0.1001 0.8624 1.0000
2.500 0.6663 0.01874 0.01113 -0.1007 0.8508 1.0000
2.750 0.7012 0.01849 0.01094 -0.1014 0.8391 1.0000
3.000 0.7365 0.01816 0.01075 -0.1019 0.8273 1.0000
3.250 0.7713 0.01776 0.01043 -0.1021 0.8147 1.0000
3.500 0.8047 0.01732 0.01009 -0.1021 0.8006 1.0000
3.750 0.8375 0.01684 0.00971 -0.1017 0.7851 1.0000
4.000 0.8707 0.01629 0.00933 -0.1013 0.7681 1.0000
4.250 0.8976 0.01597 0.00912 -0.1000 0.7447 1.0000
4.500 0.9255 0.01562 0.00884 -0.0987 0.7177 1.0000
4.750 0.9521 0.01535 0.00861 -0.0972 0.6833 1.0000
5.000 0.9766 0.01526 0.00849 -0.0954 0.6379 1.0000
5.250 0.9994 0.01544 0.00858 -0.0935 0.5814 1.0000
5.500 1.0202 0.01596 0.00884 -0.0915 0.5213 1.0000
5.750 1.0403 0.01675 0.00934 -0.0898 0.4696 1.0000
6.000 1.0606 0.01762 0.01001 -0.0883 0.4273 1.0000
6.250 1.0812 0.01849 0.01078 -0.0870 0.3916 1.0000
6.500 1.1019 0.01937 0.01160 -0.0857 0.3605 1.0000
6.750 1.1209 0.02017 0.01243 -0.0842 0.3272 1.0000
7.000 1.1335 0.02087 0.01299 -0.0819 0.2812 1.0000
7.250 1.1434 0.02161 0.01363 -0.0795 0.2132 1.0000
7.500 1.1418 0.02489 0.01572 -0.0755 0.0662 1.0000
7.750 1.1459 0.02778 0.01846 -0.0718 0.0454 1.0000
8.000 1.1570 0.02978 0.02058 -0.0691 0.0386 1.0000
8.250 1.1672 0.03236 0.02318 -0.0667 0.0343 1.0000
8.500 1.1848 0.03423 0.02525 -0.0650 0.0301 1.0000
8.750 1.2054 0.03681 0.02797 -0.0639 0.0283 1.0000
9.000 1.2288 0.03998 0.03136 -0.0630 0.0274 1.0000
9.250 1.2501 0.04357 0.03530 -0.0620 0.0273 1.0000
9.500 1.2655 0.04745 0.03964 -0.0602 0.0277 1.0000
9.750 1.2717 0.05160 0.04437 -0.0575 0.0285 1.0000
10.000 1.2693 0.05587 0.04918 -0.0543 0.0294 1.0000
10.250 1.2613 0.06005 0.05381 -0.0510 0.0303 1.0000
10.500 1.2480 0.06383 0.05794 -0.0475 0.0309 1.0000
10.750 1.2318 0.06767 0.06207 -0.0446 0.0315 1.0000
11.000 1.2138 0.07179 0.06644 -0.0425 0.0320 1.0000
11.250 1.1945 0.07627 0.07116 -0.0415 0.0324 1.0000
11.500 1.1743 0.08120 0.07630 -0.0417 0.0327 1.0000
11.750 1.1535 0.08666 0.08195 -0.0430 0.0329 1.0000
12.000 1.1318 0.09283 0.08829 -0.0456 0.0331 1.0000
12.250 1.1099 0.09981 0.09543 -0.0496 0.0333 1.0000
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Polar data table (+)
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